Computation of wing flutter for unsteady transonic flows in the frequency domain is studied in this thesis.
本文研究了机翼跨音速颤振的频域计算方法。
Combining dynamic design of wing flutter model for a giant transport aircraft, a numerical example of engineering application is presented.
结合某大型飞机机翼颤振吹风模型的动力设计，本文给出了工程应用的具体数值例子。
A local form of interface interpolation method for fluid-structure interaction problems was presented and applied to interpolation of wing flutter calculation.
提出了一种局部形式的流固耦合问题界面插值方法，并应用于机翼颤振计算的界面插值。
The computing AGARD445.6 wing flutter results validate the physical law of a typical transonic flutter "dip" with the bottom near the domain which Mach number is 1.
通过跨声速标模算例AGARD445.6机翼的颤振计算，计算的颤振临界速度与实验值有5%左右的误差，验证本方法的正确性。
The computing AGARD445.6 wing flutter results validate the physical law of a typical transonic flutter "dip" with the bottom near the domain which Mach number is 1.
通过跨声速标模算例AGARD445.6机翼的颤振计算，计算的颤振临界速度与实验值有5%左右的误差，验证本方法的正确性。
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